EP3081796A1 - Inverseur de poussée comprenant des portes pivotables - Google Patents

Inverseur de poussée comprenant des portes pivotables Download PDF

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Publication number
EP3081796A1
EP3081796A1 EP16164137.8A EP16164137A EP3081796A1 EP 3081796 A1 EP3081796 A1 EP 3081796A1 EP 16164137 A EP16164137 A EP 16164137A EP 3081796 A1 EP3081796 A1 EP 3081796A1
Authority
EP
European Patent Office
Prior art keywords
transcowl
internal door
support structure
thrust reverser
turbofan engine
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP16164137.8A
Other languages
German (de)
English (en)
Inventor
Danis Burton SMITH
Mark Knowles
Robert Romano
Shawn Alstad
David Robinson
Israel PICAZO
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Honeywell International Inc
Original Assignee
Honeywell International Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Honeywell International Inc filed Critical Honeywell International Inc
Publication of EP3081796A1 publication Critical patent/EP3081796A1/fr
Withdrawn legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers
    • F02K1/605—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers the aft end of the engine cowling being movable to uncover openings for the reversed flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/64—Reversing fan flow
    • F02K1/70—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing
    • F02K1/72—Reversing fan flow using thrust reverser flaps or doors mounted on the fan housing the aft end of the fan housing being movable to uncover openings in the fan housing for the reversed flow
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Definitions

  • the present invention relates to a thrust reverser system for a turbofan engine, and more particularly to a thrust reverser system in which an internal door has a pivot axis aft of the reverse flow path of the turbofan engine.
  • turbofan engines on most jet-powered aircraft include thrust reversers. Thrust reversers enhance the stopping power of the aircraft by redirecting the turbofan engine exhaust airflow in order to generate reverse thrust.
  • the thrust reverser When stowed, the thrust reverser typically forms a portion the engine nacelle and forward thrust nozzle. When deployed, the thrust reverser typically redirectsat least a portion of the airflow (from the fan and/or engine exhaust) forward and radially outward, to help decelerate the aircraft.
  • Thrust reverser designs are commonly known, and the particular design utilized depends, at least in part, on the engine manufacturer, the engine configuration, and the propulsion technology being used. Thrust reverser designs used most prominently with turbofan jet engines fall into two general categories: (1) fan flow thrust reversers, and (2) mixed flow thrust reversers. Fan flow thrust reversers affect only the airflow discharged from the engine fan. Whereas, mixed flow thrust reversers affect both the fan airflow and the airflow discharged from the engine core (engine airflow).
  • Fan flow thrust reversers are typically used on relatively high-bypass ratio turbofan engines.Fan flow thrust reversers include so-called “Cascade-type” or “Translating Cowl-type”thrust reversers.Fan flow thrust reversers generally wrap circumferentially around the engine core aft of the engine fan and, when deployed, redirect fanairflow through a plurality of cascade vanes disposed within an aperture of a reverse flow path. Typically, fan flow thrust reverser designs include one or more translating sleeves or cowls (“transcowls”) that, when deployed, open an aperture, expose cascade vanes, and create a reverse flow path. Fan flow reversers may also include so-called pivot doors or blocker doors which, when deployed, rotate to block the forward thrust flow path.
  • transcowls translating sleeves or cowls
  • mixed flow thrust reversers are typically used with relatively low-bypass ratio turbofan engines.
  • Mixed flow thrust reversers include so-call “Target-type,” “Bucket-type,” and “Clamshell Door-type” thrust reversers.
  • Mixed flow thrust reversers typically use two or morepivoting doors that rotate, simultaneously opening a reverse flow path through an aperture and blocking the forward thrust flow path.
  • Mixed flow thrust reversers are necessarily located aft or downstream of the engine fan and core, and often form the aft part of the engine nacelle.
  • Fan flow thrust reversers are most suitable for use with relatively high-bypass ratio engines,because(i) adequate decelerating force can be achieved by redirecting only the fan flow, and (ii) the fan flow thrust reverser components are not exposed to the relatively high temperatures of the engine core exhaust.By comparison, mixed flow thrust reversers are most suitable for use with relatively low-bypass ratio engines, which typically require the redirection of both the fan airflow and the engine core airflow in order to achieve an adequate decelerating force.
  • a thrust reverser system for a turbofan engine comprises: a support structure configured to be mounted to the turbofan engine; a transcowl mounted on the support structure and comprising a front edge, the transcowl movable between a first position, in which the front edge abuts the support structure, and a second position, in which an aperture is formed between the front edge and the support structure; and a first displaceable internal door pivotally mounted to the support structure and at least partially surrounded by the transcowl, the first displaceable internal door rotatable about a pivot axis and configured to be pivoted between a stowed position and a deployed position when the transcowl moves between the first position and the second position, respectively, the first displaceable internal door configured, when it is in the deployed position, to redirect engine airflow through the aperture to thereby generate reverse thrust, wherein the pivot axis is positioned aft of the front edge when the transcowl is in the second position.
  • the thrust reverser system comprises: an annular support structure configured to be mounted the turbofan engine, the annular support structure comprising a circumferentially located opening; a transcowl mounted on the support structure and forming a portion of a nacelle aft of the turbofan engine, the transcowl movable between a first position, in which a front edge of the transcowl abuts the support structure, and a second position, in which an aperture is formed between the front edge and the support structure; and a first displaceable internal door pivotally mounted to the support structure and at least partially surrounded by the transcowl, the first displaceable internal door rotatable about a pivot axis and configured to be pivoted between a stowed position and a deployed position when the transcowl moves between the first position and the second position, respectively, the first displaceable internal door configured, when it is in the deployed position, to redirect engine airflow through the aperture to thereby generate reverse thrust, where
  • a turbofan engine comprises: a thrust reverser system that comprises: a support structure configured to be mounted to the turbofan engine; a transcowl mounted on the support structure and comprising a front edge, the transcowl movable between a first position, in which the front edge abuts the support structure, and a second position, in which an aperture is formed between the front edge and the support structure; and a first displaceable internal door pivotally mounted to the support structure and at least partially surrounded by the transcowl, the first displaceable internal door rotatable about a pivot axis and configured to be pivoted between a stowed position and a deployed position when the transcowl moves between the first position and the second position, respectively, the first displaceable internal door configured, when it is in the deployed position, to redirect engine airflow through the aperture to thereby generate reverse thrust, wherein the pivot axis is positioned aft of the front edge when the transcowl is in the second position.
  • Various embodiments are directed to a hybrid thrust reverser system suitable for an aircraft turbofan engine, and methods for producing the same.
  • the exemplary embodiments advantageously provide improvements in efficiency over previously proposed hybrid thrust reverser designs.
  • cascade vanes may be necessary to achieve adequate and efficient reverse thrust performance for the target applications.
  • reverse thrust efficiency may be increased with internal doors that pivot into a deployed position without interfering with either an aperture used for a reverse flow path or any cascade vanes located therein.
  • the embodiments described below are merely examples and serve as a guide for implementing the novel systems and methods herein on any industrial, commercial, military, or consumer turbofan application. As such, the examples presented herein are intended as non-limiting.
  • FIGS. 1 -3 are perspective views of a traditional aircraft turbofan engine with (i) a fan flow thrust reverser in a stowed position ( FIG. 1 ), (ii) a mixed flow thrust reverser in a stowed position ( FIG. 2 ), and (iii) a mixed flow thrust reverser in a deployed position ( FIG. 3 ).
  • the turbofan engine is substantially encased within an aerodynamically smooth outer covering, the nacelle 100 ,which wraps around the turbofan engine.
  • the nacelle 100 also extends aft from the turbofan engine, forming an aerodynamically shaped downstream portion having a cavity providing the engine exhaust flow path when the aircraft is producing forward thrust.
  • Annular translatable cowl, or transcowl 102 is positioned circumferentially, forming a portion of the nacelle 100.
  • FIG. 2 depicts a traditional mixed flow thrust reverser in a stowed (first) position
  • FIG. 3 depicts the traditional mixed flow thrust reverser in a deployed (second) position
  • Ambient air 104 enters the turbofan engine and passes through a fan 106.
  • Ambient air 104 is split into a portion that is pressurized, mixed with fuel and ignited, generating hot gasses 108.
  • Another portion of ambient air 104 often referred to as "fan air” 110 only passes through the fan.
  • the fan air 110 and hot gasses 108 become turbofan engine exhaust 112.
  • doors 114 are stowed, and in FIG. 3 the doors 114 are deployed. When the doors 114 are deployed, they may abut at center 116. Deployed doors 114 create a reverse flow path 118.
  • FIGS. 4-6 provide simplified three-dimensional images of exemplary embodiments of thrust reverser systems with some cascade-type thrust reverser features.
  • FIG. 4 and FIG. 5 provide three dimensional images of a thrust reverser system 200 with transcowl 102 in a stowed (first) position ( FIG.4 ), and in a deployed (second) position ( FIG.5 ).
  • a thrust reverser centerline 207 is depicted, along which the turbofan engine exhaust airflow 205 travels.
  • Transcowl 102 forms the downstream portion of the nacelle 100 (described hereinabove), bounding the turbofan engine exhaust airflow 205.
  • turbofan engine exhaust airflow 205 enters through a forward side 203 of thrust reverser system 200.
  • transcowl 102 In a stowed (first) position, the front edge 304 of transcowl 102 abuts circumferentially with a portion of an annular support structure that includes an annular front flange 202 and one or more side beams 306 ( FIG. 5 ).
  • the front edge 304 of transcowl 102 exposes an aperture 302 that is bounded on one side by front edge 304 ( FIG. 5 ).
  • deploying transcowl 102 results in redirecting turbofan engine exhaust airflow 205 through aperture 302; redirected engine airflow is often referred to as reverse thrust, or an active reverse flow path.
  • Cascade-type thrust reverser features, such as a plurality of cascade vanes, disposed within the aperture 302, may be included in some embodiments ( FIG. 6 ).
  • the front flange 202 and associated side beams 306 provide a rigid annular support structure to which moveable thrust reverser components (described in detail below) may be mounted.
  • the front flange 202 portion of the annular support structure also serves to mount the entire thrust reverser system 200 to the turbofan engine.
  • the inner surface 210 of the downstream portion of the nacelle 100 is typically formed by the inner surface of transcowl 102; which is machined or manufactured to be smooth, free of blisters, pits, seams, or edges, machined to be a substantially continuous circumferential surface. It typically forms a bounded volumetric cavity that becomes the engine exhaust flow path in forward thrust mode. Accordingly, the one or more side beams 306 are preferably machined or manufactured to slidably engage with the transcowl 102 such that they are disposed substantially continuous with the inner surface 210, thereby (i) minimizing disruption of the smoothness of the inner surface 210 and (ii) not introducing interference into the engine exhaust flow path.
  • FIG. 6 is a three dimensional image of a thrust reverser system of FIG. 4 having atranscowl in a deployed (second)position, according to another exemplary embodiment.
  • the embodiment of FIG. 6 depicts a plurality of cascade vanes 402 disposed within the reverse flow path at the aperture 302.
  • the transcowl 102 translates from the stowed (first) position to the deployed (second) position as previously described.
  • transcowl 102 covers the plurality of cascade vanes 402, and when deployed, transcowl 102 exposes the cascade vanes 402.
  • the cascade vanes are shaped and oriented to direct turbofan engine exhaust airflow 205 through the aperture 302 when the reverse flow path is active.
  • the number, position, size, material, etc., of the cascade vanes 402 are dependent upon the individual thrust reverser system design.
  • FIGS 7-10 introduce displaceable internal doors to the cascade-type features already described.
  • transcowl 102 When transcowl 102 is stowed, internal doors are stowed, and when the thrust reversers are commanded to deploy, transcowl 102 moves aft, causing one or morepivotally mounted internal doors to pivot into a deployed position.
  • the one or more internal doors block the aft directed turbofan engine exhaust airflow 205 that had been passing through the cavity bounded by the continuous inner surface 210, thereby redirecting turbofan engine exhaust airflow 205 (directing it forward and radially), creating an active reverse flow path through the aperture 302.
  • the re-direction of turbofan engine exhaust airflow 205 creates a reverse thrust and, thus, works to slow the aircraft.
  • FIG. 7 and FIG. 8 are partial cross sectional views, above a thrust reverser centerline 207 , of a thrust reverser system 500 having the transcowlin a stowed position ( FIG. 7 ) and in a deployed position ( FIG. 8 ), according to an exemplary embodiment.
  • FIG. 7 and FIG. 8 also depict an actuator 502, whichis a movable thrust reverser component that causes transcowl 102 to move.
  • the actuator 502 is mounted to front flange 202 and coupled to transcowl 102 . When actuator 502 extends, it causes the transcowl 102 to translate from the stowed (first) position to the deployed (second) position. Actuator 502 also retracts and returns transcowl 102 from the deployed position to the stowed position.
  • Actuator 502 may comprise mechanical and/or electrical components, and may be responsive to aircraft engine system commands.
  • FIG. 7 is a partial cross sectional view, above a thrust reverser centerline 207, of a thrust reverser system 500 having the transcowl 102 in a stowed position, according to an exemplary embodiment.
  • Internal door 505 is pivotally mounted to side beam 306 at pivot joint 506 to allow internal door 505 to pivot about a pivot axis 510 .
  • internal door 505 is shown with edge 504 substantially continuous with inner surface 508.
  • the cross sectional view of FIG. 7 may make internal door 505 appear to be two-dimensional, in practice it may be three-dimensional, for example, a clamshell shape.
  • Internal door 505 is machined or manufactured to have a shape that permits it to be substantially continuous with the inner surface 508 of transcowl 102 while stowed, minimizing interference with turbofan engine exhaust airflow 205.
  • FIG. 8 is a partial cross sectional viewof the thrust reverser system in FIG. 7 having the transcowl 102 in a deployed position, according to the exemplary embodiment.
  • Actuator 502 is shown extended, and internal door 505 has pivoted into its deployed position.
  • Internal door 505 is machined or manufactured to have a shape that permits it to obstruct turbofan engine exhaust airflow 205 and redirect it forward when internal door 505 is in its deployed position.
  • internal door 505 can be seen to have deployed; it has moved to obstruct turbofan engine exhaust airflow 205 , directing it through aperture 302, creating reverse flow path 604.
  • pivot axis 510 is located a distance 606 downstream (aft) of the front edge 304 of the transcowl 102 when it is in its deployed (second) position.
  • the location of pivot joint 506 provides pivot axis 510 that prevents the internal door 505, when deployed, from obstructing or interfering with reverse flow path 604 and/or aperture 302.
  • Pivot joint 506 may be any fastener or fastening assembly capable of enabling the internal door 505 to pivot as described while meeting all attending design requirements. As one with skill in the art will appreciate, various embodiments of pivotally mounted internal doors are supported.
  • FIG. 9 and FIG. 10 are partial cross sectional views of a thrust reverser system 700, according to another exemplary embodiment.
  • the cross sectional views in FIG. 9 and FIG. 10 also depict a portion of thrust reverser system 700 above thrust reverser centerline 207.
  • Internal door 704 is pivotally mounted to side beam 702 at pivot joint 706. As in FIG. 9 and FIG. 10 , when transcowl 102 is stowed, internal door 704 is stowed, and when transcowl 102 is deployed, internal door 704 is deployed.
  • Actuator 502 functions as described above.
  • internal door 704 is shown in its stowed position, with edge 708 substantially continuous with inner surface 508.
  • the cross sectional view of FIG. 9 may make internal door 704 appear to be two-dimensional, in practice it may be three-dimensional, for example, a clamshell shape.
  • Internal door 704 is machined or manufactured to have a shape that permits it to be substantially continuous with the inner surface 508 of transcowl 102 while stowed.
  • FIG. 10 is a partial cross sectional viewof the thrust reverser system in FIG. 9 having the transcowl 102 in a deployed position, according to the exemplary embodiment.
  • Actuator 502 is shown extended, and internal door 704 has pivoted, about its pivot axis 710, into its deployed position, blocking turbofan engine exhaust airflow 205.
  • Internal door 704 is machined or manufactured to have a shape that permits it to obstruct turbofan engine exhaust airflow 205 and redirect it forward when internal door 704 is in its deployed position.
  • internal door 704 can be seen to have deployed; it has moved to obstruct turbofan engine exhaust airflow 205 , directing it through aperture 302, creating reverse flow path 806.
  • pivot axis 710 As the internal door 704 pivots about the pivot axis 710, it traces out a path that inner surface 508 is modified to accommodate.
  • the contoured area 804, depicted in FIG. 10 is formed within inner surface 508 to provide clearance of internal door 704 as it pivots about the pivot axis 710 provided by pivot joint 706.
  • pivot axis 710 is located a distance 802 downstream (aft) of the front edge 304 of the transcowl 102 when it is in its deployed (second) position.
  • the location of pivot joint 706 provides a pivot axis 710 that prevents the internal door 704, when deployed, from obstructing or interfering with reverse flow path 806 and/or aperture 302.
  • Pivot joint 706 may be any fastener or fastening assembly capable of enabling the internal door 704 to pivot as described while meeting all attending design requirements.
  • FIG. 8 provides a first-pass visual understanding of the relationship between the locations of the pivot axes (provided by the pivot joints), the shape of the inner door, and the size and shape of the associated contour formed within the inner surface.
  • the pivot joints (506, 706) provide a pivot axis (510, 710) that is aft of the front edge 304 of the transcowl 102 .
  • the location of pivot joints (506, 706) and the shape of the internal doors are designed to ensure that the internal doors themselves are completely out of the way of the reverse flow path (806,604) when the internal doors are deployed (i.e., when transcowl 102 is in its deployed (second) position).
  • the pivot axis may be placed in a variety of locations aft of the front edge 304 while still satisfying these design guidelines, for example the location of pivot axis 510 is more aft than the location of pivot axis 710.
  • the distance aft of the front edge 304 that a given pivot joint is located (for example, 606 and 802 ) is design specific and informs additional design decisions regarding the shape of the internal doors and the associated shape and size of the contoured area (804, 602) formed, typically by machining, within the inner surface 508.
  • the shape, material and size of the internal doors may be further modified with openings in order to provide clearance forone or more actuators and/or mechanisms employed to couple a respective internal door to a respectivetranscowl.
  • Opening 712 shown in FIG. 9 and FIG. 10 , provides a two-dimensional view of an opening in internal door 704 that is configured to accommodate the actuator 502 as internal door 704 pivots.
  • the hybridized thrust reverser embodiments described herein combine internal doors, unobstructed reverse flow paths, and cascade vanes.
  • the combinations of features presented advantageously provide a thrust reverser system capable of providing enhanced reverse thrust performance while reducing weight, cost, and complexity.
  • an embodiment of a system or a component may employ various integrated circuit components, e.g., memory elements, digital signal processing elements, logic elements, look-up tables, or the like, which may carry out a variety of functions under the control of one or more microprocessors or other control devices.
  • integrated circuit components e.g., memory elements, digital signal processing elements, logic elements, look-up tables, or the like, which may carry out a variety of functions under the control of one or more microprocessors or other control devices.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP16164137.8A 2015-04-16 2016-04-06 Inverseur de poussée comprenant des portes pivotables Withdrawn EP3081796A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14/688,779 US20160305370A1 (en) 2015-04-16 2015-04-16 Translating cowl thrust reverser with door pivots aft of reverse flow path

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EP3081796A1 true EP3081796A1 (fr) 2016-10-19

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EP16164137.8A Withdrawn EP3081796A1 (fr) 2015-04-16 2016-04-06 Inverseur de poussée comprenant des portes pivotables

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Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2564891A (en) * 2017-07-26 2019-01-30 Short Brothers Plc Nacelle with thrust reverser
US10451002B2 (en) 2016-01-22 2019-10-22 Honeywell International Inc. Translating cowl thrust reverser that prevents unintended door rotation

Families Citing this family (5)

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Publication number Priority date Publication date Assignee Title
US10436112B2 (en) * 2017-06-26 2019-10-08 The Boeing Company Translating turning vanes for a nacelle inlet
US10343786B2 (en) 2017-06-28 2019-07-09 General Electric Company System and method of operating a ducted fan propulsion system during aircraft taxi
US10865737B2 (en) 2017-08-29 2020-12-15 Honeywell International Inc. Hidden linkage for a translating cowl thrust reverser
US10794327B2 (en) 2018-03-21 2020-10-06 Honeywell International Inc. Systems and methods for thrust reverser with temperature and fluid management
US11002222B2 (en) 2018-03-21 2021-05-11 Honeywell International Inc. Systems and methods for thrust reverser with temperature and fluid management

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US3050937A (en) * 1958-06-09 1962-08-28 Boeing Co Reversible thrust jet engines and controls therefor
US3262270A (en) * 1965-06-07 1966-07-26 Gen Electric Thrust reverser
DE1287444B (de) * 1965-06-07 1969-01-16 Gen Electric Schubumkehrvorrichtung fuer ein Mantelstromstrahltriebwerk
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Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10451002B2 (en) 2016-01-22 2019-10-22 Honeywell International Inc. Translating cowl thrust reverser that prevents unintended door rotation
GB2564891A (en) * 2017-07-26 2019-01-30 Short Brothers Plc Nacelle with thrust reverser
US11230994B2 (en) 2017-07-26 2022-01-25 Short Brothers Plc Nacelle with thrust reverser

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